Abstract: A turbine element airfoil has a cooling passageway network with a slot extending from a trailing passageway toward the trailing edge. A number of discrete posts span the slot between pressure and suction sidewall portions. A trailing array of the posts are spaced ahead of an outlet of the slot.

Abstract: A turbine engine component has an airfoil portion with a suction side. The component includes a cooling microcircuit embedded within a wall structure forming the suction side. The cooling microcircuit has at least one cooling film hole positioned ahead of a gage point for creating a flow of cooling fluid over an exterior surface of the suction side which travels past the gage point. The cooling microcircuit is formed using refractory metal core technology. A method for forming the cooling microcircuit is described.